• Journal of the Korea Academia-Industrial cooperation Society
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• v.8 no.5
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• pp.984-990
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• 2007

The objective of this study is the estimation of the $O_2$ concentration range, the thermal behavior by high temperature exhaust gas and durability of exhaust manifold by the coupling analysis of CFD and structure analysis. This estimation results is used the guideline to the optimum design of exhaust manifold.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.56 no.4
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• pp.395-406
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• 2020

The objectives of this study were to develop the optimal structures of recirculating aquaculture tank for improving the removal efficiency of solid materials and maintaining water quality conditions. Flow analysis was performed using the CFD (computational fluid dynamics) method to understand the hydrodynamic characteristics of the circular tank according to the angle of inclination in the tank bottom (0°, 1.5° and 3°), circulating water inflow method (underwater, horizontal nozzle, vertical nozzle and combination nozzle) and the number of inlets. As the angle in tank bottom increased, the vortex inside the tank decreased, resulting in a constant flow. In the case of the vertical nozzle type, the eddy flow in the tank was greatly improved. The vertical nozzle type showed excellent flow such as constant flow velocity distribution and uniform streamline. The combination nozzle type also showed an internal spiral flow, but the vortex reduction effect was less than the vertical nozzle type. As the number of inlets in the tank increased, problems such as speed reduction were compensated, resulting in uniform fluid flow.

• Journal of the Korea Institute of Military Science and Technology
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• v.21 no.1
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• pp.10-16
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• 2018

The Republic of Korea Marine Corps is planning to develop a new amphibious assault vehicle which is able to operate with higher water speed than current KAAV. In order to achieve a higher water speed for hydrodynamically bulff-body vehicles, it is essential to develop drag reduction strategies. In this paper, resistance characteristics including trim angles of amphibious assault vehicles with several appendage designs are investigated using a commercial CFD code, STAR-CCM+. The computed results are compared with experimental data conducted at the towing tank with 1:4.5 scaled model and show good correlation. Comparing with the results of bare hull, 3.4 % of hydrodynamic drag and 52 % of trim angle are reduced by the application of double angled bow flap and a hydrofoil attached at the transom.

• Journal of the Korea Institute of Military Science and Technology
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• v.23 no.4
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• pp.363-370
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• 2020

In this study, pitching stability derivatives of the conical shell configuration is predicted using commercial CFD code. Unsteady flow analysis with forced harmonic motion of the model is performed using overset mesh. The test is conducted about Basic finner missile configuration. The static and dynamic stability derivatives are good agreement with available experimental data. As the same way, a conical shell is analyzed in Mach number 1.6 and various reduced frequency. The static and dynamic derivatives are obtained from the time-pitching moment coefficient histories in each of four cases of mean angle of attack. The variation of reduced frequency is not affected static and dynamic derivatives. Increasing the mean angle of attack, static derivatives are increased slowly. Comparison of the Cm curves at the steady and unsteady state results shows that the Cm curve including the damping effect is lower than otherwise case, approximately 9-18 %.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.20-27
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• 2002

Aircraft design requires the intergration of several disciplines, inculding aerodynamics, structures, controls. To achieves advances in performance, each technology, or discipline must be more accurate in analysis and must be more highly intergrated. One of the important interdisciplinary interactions in mordern aircraft design is that of aerodynamics and structures. In this study, for increasing accuracy in each discipline's analysis, CFD for aerodynamic analysis and FEM for structurral analysis was used and, for considering important interdisciplinary interactions, aeroelastic effect was considered. As optimization algorithm, PBIL algorithm was used for global optima and was parallelized to alleviate the computational burden. The efficiency and accuracy of the present method was assesed by range maximiziation of reference of reference wing.

• Transactions of the Korean hydrogen and new energy society
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• v.30 no.2
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• pp.147-154
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• 2019

In this study, effects of flow types and size of molten carbonate fuel cells (MCFCs) were investigated using CFD simulation. In the simulation, the current collector of MCFCs were assumed to be an porous media. With the area of $0.09m^2$, the effect of flow types such as Co-flow, Counter-flow, Cross-flow were studied. After that the effect of the size and flow direction was studied. Among three-flow types, MCFCs with co-flow type shows more uniform distribution and current density distribution.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.5-8
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• 2012

임계마하수란 에어포일의 표면에서 음속에 도달하는 부분이 생기기 시작하는 가장 낮은 Mach number라 한다. 임계마하수는 천음속에서 자유류가 임계마하수보다 조금 커지면 항력이 급격하게 증가하게 된다. 그렇기 때문에 임계마하수가 큰 에어포일이 천음속 항공기 설계에 있어서 매우 중요한 역할을 하게 된다. 이번 연구는 학부과정에서 배운 임계마하수에 대해 정의하고, EDISON_CFD를 이용하여 에어포일에 따라서 임계마하수가 달라지는 것을 확인해 보았다. 그 결과 에어포일이 두꺼워질수록 낮은 마하수에서 Shock이 발생하는 것을 확인할 수 있었다. 마지막으로 EDISON_CFD를 이용하여 계산된 임계마하수 값과 이론값을 비교한 결과, 높은 정확도를 확인할 수 있었다.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.85-88
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• 2012

루프 페어링은 화물차의 주행저항 및 유도항력을 줄이기 위해 설치되는 장치 중 하나이다. 이 장치는 화물차의 지붕 윗부분에 설치하여 화물차가 받는 항력을 줄이는데 사용이 된다. 이번 과제에서는 루프 페어링의 효과에 대해 유체역학적인 증명 및 확인을 위해 루프 페어링의 설치 전-후 트럭의 형상에 따른 유동의 변화와 항력계수의 값을 EDISON CFD를 사용하여 구한 후 각각 비교 하였다. 이를 위해 EDISON CFD의 압력 contour와 stream line, 정압계수(Cp)그래프를 통해 트럭의 주행 중 발생하는 박리현상을 가시적으로 확인하였고, 항력계수(Cd)값을 비교하는 것을 통해 루프 페어링을 설치한 경우가 미설치된 경우보다 주행 시 더욱 유리하다는 것으로 결론을 내렸다.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.97-100
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• 2012

항력계수와 양력계수는 각각 항력, 양력을 동압과 에어포일의 코드 길이로 나눈 값으로 정의된다. 항공기의 비행에 있어서 항력과 양력은 매우 중요한 요소로 작용하며 항공기의 속도에 따라 항력과 양력은 크게 변하게 된다. 첫째로 학부과정에서 배운 마하수에 따른 항력계수의 변화, 그 중에서도 마하수 1 이상에서의 항력계수 감소에 관한 이론을 살펴보고 EDISON_CFD를 이용하여 마하수에 따른 항력계수의 값을 실제로 측정해보고 비교해보았다. 두 번째로는 EDISON_CFD로 측정한 마하수버에 따른 양력계수 값과 앞서 측정한 항력계수 값을 이용하여 NACA0012의 마하수에 따른 양력과 항력의비 (양항비)를 구하여 실제고도에서 비행 시 NACA0012의 적정 효율을 가지는 마하수를 알아보았다.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.9-12
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• 2012

현재 각 나라에서 고고도 무인항공기에 대한 관심이 높아지고, 우리나라 또한 여러 가지 형상의 고고도 무인항공기를 개발하기위해 노력하고 있다. 본 연구에서는 고고도 무인항공기에 사용되는 에어포일의 공력특성을 EDISON_CFD를 이용하여 분석하였다. 현재 개발된 고고도 무인항공기 중 글로벌 호크를 선정하여 그 주 날개의 Airfoil을 해석모델로 선정하고 항공기 운항시 고도 조건을 적용하여 공력특성을 분석하였다. 받음각의 범위는 $2^{\circ}{\sim}10^{\circ}$로 설정하였고 $C_l$ 및 $C_d$ 값을 계산하여 공력 특성 곡선($C_l$, $C_d$, $C_d-C_l$)을 구성하였다.